CN110284929A - A kind of turbine casing seal structure - Google Patents
A kind of turbine casing seal structure Download PDFInfo
- Publication number
- CN110284929A CN110284929A CN201910655984.XA CN201910655984A CN110284929A CN 110284929 A CN110284929 A CN 110284929A CN 201910655984 A CN201910655984 A CN 201910655984A CN 110284929 A CN110284929 A CN 110284929A
- Authority
- CN
- China
- Prior art keywords
- piece
- guide vane
- turbine casing
- pin
- obturage
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/005—Sealing means between non relatively rotating elements
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The application belongs to casing seal structure design field, in particular to a kind of turbine casing seal structure.It include: to obturage piece, backboard and pin.The first end of guide vane has the interconnecting piece cooperated with high-pressure turbine casing, and the interconnecting piece offers pin hole, and the second end of the guide vane connects low-pressure turbine casing；It obturages piece and matches with the guide vane and arrange multiple, the piece of obturaging includes obturaging portion and holding out against portion for L-shaped setting, and the portion of obturaging connects the interconnecting piece and the high-pressure turbine casing of the guide vane, and the portion of holding out against abuts the guide vane；Backboard be arranged in it is two neighboring it is described obturage the obturaging in portion of piece, obturage gas leakage between portion for obturage piece described in preventing two；Pin is for obturage portion and the backboard for obturaging piece to be fixedly connected with the guide vane interconnecting piece.The application is fitted closely using chip architecture guarantee is obturaged, and pin is being obturaged near contact position fixed, obturages that effect is good, and arrangement works are reliable.
Description
Technical field
The application belongs to casing seal structure design field, in particular to a kind of turbine casing seal structure.
Background technique
Seal structure design between high and low pressure turbine casing must be studied in the design of aero-turbine structure
Problem is played in work and is obturaged between high and low pressure turbine casing, prevents cold air from revealing, guarantee the work of engine operating efficiency
With.
Seal structure commonly used in the prior art, which is elastic clip, obturages form with obturage that chip architecture combines.As shown in Figure 1,
Elastic clip 10 is assembled on turbine casing 13, is stepped up using the positioning of the first pin 11, first obturages piece 8, and to be assemblied in casing pre-
It in the space stayed, is adjacent on one side with casing 7, another side realizes axial restraint by 10 elasticity of elastic clip, to prevent from circumferentially obturaging piece
Between generate gas leakage because of gap, gap location, which increases, second obturages piece 9 at one, obturages piece and circumferentially leans on 12 anti-rotation of the second pin, anti-rotation
Second pin 12 is fixed on casing.The prior art has the disadvantage in that obturaging piece reliably working needs elastic clip to be always maintained at
Elastic stage, and elastic clip multiple thermodynamic cycle work after there are structural failure risks, effect is entirely obturaged after failure by nothing
Method guarantees, and certain engine transition states cause elastic clip elastic force to be not enough to support and obturage piece and lead to gas leakage there are pressure difference is larger
Occur；Obturaging piece leans on pin to realize circumferential anti-rotation, needs two pin locating holes being designed to that one is to guarantee that assembly is reachable
Circular hole, one be runway hole, bayonet fittings gap is excessive, and there are gas leakage hidden danger, obturage ineffective；Elastic clip obturages piece and has two
The positioning of kind of pin, number of parts is more, and processing technology is complicated, at high cost, linkage editor is complicated.
Thus, it is desirable to have a kind of technical solution overcomes or at least mitigates at least one drawbacks described above of the prior art.
Summary of the invention
There is provided a kind of turbine casing seal structures for the purpose of the application, to solve existing in the prior art at least one
A problem.
The technical solution of the application is:
A kind of turbine casing seal structure, comprising:
Guide vane, the first end of the guide vane have the interconnecting piece cooperated with high-pressure turbine casing, the connection
Portion offers pin hole, and the second end of the guide vane connects low-pressure turbine casing；
Obturage piece, it is described obturage piece and match with the guide vane arrange multiple, the piece of obturaging includes L-shaped setting
Obturage portion and hold out against portion, the portion of obturaging connects the interconnecting piece and the high-pressure turbine casing of the guide vane, the top
Tight portion abuts the guide vane；
Backboard, the backboard be arranged in it is two neighboring it is described obturage the obturaging in portion of piece, for obturaging described in preventing two
Piece obturages gas leakage between portion；
Pin, the pin is for consolidating obturage portion and the backboard for obturaging piece with the guide vane interconnecting piece
Fixed connection.
Optionally, one end of the backboard has bending part, and the end for obturaging portion of piece is obturaged described in the bending part cladding
Portion.
Optionally, one end of the pin has cap head, and the diameter of the cap head is greater than the pin hole of the interconnecting piece
Diameter.
Optionally, the other end of the pin is realized by flaring and is fixed.
Optionally, the other end of the pin is realized by welding and is fixed.
At least there are following advantageous effects in invention:
The turbine casing seal structure of the application is obturaged chip architecture guarantee using elasticity and fitted closely, sealed using pin
Tight contact position is fixed nearby, obturages that effect is good, and arrangement works are reliable.
Detailed description of the invention
Fig. 1 is the seal structure schematic diagram of the prior art；
Fig. 2 is the turbine casing seal structure schematic diagram of one embodiment of the application；
Fig. 3 is that Fig. 2 obturages piece A direction view.
Wherein:
1- low-pressure turbine casing；2- backboard；3- obturages piece；4- high-pressure turbine casing；5- pin；6- guide vane；7- machine
Casket；8- first obturages piece；9- second obturages piece；10- elastic clip；The first pin of 11-；The second pin of 12-；13- turbine casing.
Specific embodiment
To keep the purposes, technical schemes and advantages of the application implementation clearer, below in conjunction in the embodiment of the present application
Attached drawing, technical solutions in the embodiments of the present application is further described in more detail.In the accompanying drawings, identical from beginning to end or class
As label indicate same or similar element or element with the same or similar functions.Described embodiment is the application
A part of the embodiment, instead of all the embodiments.The embodiments described below with reference to the accompanying drawings are exemplary, it is intended to use
In explanation the application, and it should not be understood as the limitation to the application.Based on the embodiment in the application, ordinary skill people
Member's every other embodiment obtained without creative efforts, shall fall in the protection scope of this application.Under
Face is described in detail embodiments herein in conjunction with attached drawing.
In the description of the present application, it is to be understood that term " center ", " longitudinal direction ", " transverse direction ", "front", "rear",
The orientation or positional relationship of the instructions such as "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outside" is based on attached drawing institute
The orientation or positional relationship shown is merely for convenience of description the application and simplifies description, rather than the dress of indication or suggestion meaning
It sets or element must have a particular orientation, be constructed and operated in a specific orientation, therefore should not be understood as protecting the application
The limitation of range.
1 to Fig. 3 the application is described in further details with reference to the accompanying drawing.
This application provides a kind of turbine casing seal structures, comprising: obturages piece 3, backboard 2 and pin 5.
Specifically, the first end of guide vane 6 has the interconnecting piece cooperated with high-pressure turbine casing 4, interconnecting piece is offered
The second end of pin hole, guide vane 6 connects low-pressure turbine casing 1；Obturage piece 3 match with guide vane 6 arrange it is multiple,
Obturaging piece 3 includes that obturaging for L-shaped setting and holds out against portion at portion, and the portion of obturaging connects the interconnecting piece and pressure turbine of guide vane 6
Casket 4, the portion of holding out against abut guide vane 6；Backboard 2 be arranged in it is two neighboring obturage the obturaging in portion of piece 3, for preventing two to obturage
Piece 3 obturages gas leakage between portion；Obturage portion and the backboard 2 that pin 5 is used to obturage piece 3 are fixed with 6 interconnecting piece of guide vane
Connection.Obturaging piece 3, opening size is slightly larger than the corresponding fit dimension of guide vane 6 in a free state, is assembled to by elasticity
It can guarantee to fit closely with guide vane 6 and 4 mating surface of high-pressure turbine casing behind position, guarantee air-tightness.
The turbine casing seal structure of the application, by the way that backboard 2 is mounted on the two neighboring gap for obturaging 3 circumferential direction of piece
Place, guarantee is circumferential air tight, realizes and positions by pin 5.Advantageously, in the present embodiment, by backboard 2 after 5 reaming of pin
Upper end bending package obturages piece 3, can increase the local stiffness for obturaging piece 3 in this way, prevent engine transition state pressure from changing
It acutely causes to obturage piece 3 and high-pressure turbine casing 4 disengages, cause to obturage and fail in short-term.
The turbine casing seal structure of the application obturages the assembly of piece 3 and realizes positioning, the cap of pin 5 by pin 5 afterwards in place
Head diameter is greater than the opening diameter of the pin hole of the interconnecting piece of guide vane 6, it is ensured that is absolutely sealed, mainstream combustion gas can not enter
It invades.Backboard 2 and obturage piece 3 assembly in place after, pin 5 can realize fastening by way of being flared or welding.Pass through pin 5
Positioning, fastening effect are played, number of components is few, and structure process is simple, and processing cost is low, is easily assembled, and better tightness, economical
Cost is relatively low.
The turbine casing seal structure of the application is obturaged chip architecture guarantee using elasticity and fitted closely, sealed using pin
Tight contact position is fixed nearby, and backboard end has wrapped up elasticity and obturaged piece, increases local stiffness, and it is good to obturage effect, structure work
Make reliable.The application realizes positioning, fastening by pin, and design of part is simple, good manufacturability, at low cost, and number of components is reduced
20% or more, assembly process process is good.
The above, the only specific embodiment of the application, but the protection scope of the application is not limited thereto, it is any
Within the technical scope of the present application, any changes or substitutions that can be easily thought of by those familiar with the art, all answers
Cover within the scope of protection of this application.Therefore, the protection scope of the application should be with the scope of protection of the claims
It is quasi-.
Claims (5)
1. a kind of turbine casing seal structure characterized by comprising
Guide vane (6), the first end of the guide vane (6) has the interconnecting piece cooperated with high-pressure turbine casing (4), described
Interconnecting piece offers pin hole, and the second end of the guide vane (6) connects low-pressure turbine casing (1)；
Obturage piece (3), it is described obturage piece (3) and match with the guide vane (6) arrange multiple, the piece (3) of obturaging includes
Portion and the portion that holds out against are obturaged in L-shaped setting, and the portion of obturaging connects the interconnecting piece and the high-pressure turbine of the guide vane (6)
Casing (4), the portion of holding out against abut the guide vane (6)；
Backboard (2), the backboard (2) setting it is two neighboring it is described obturage the obturaging in portion of piece (3), for preventing described in two
That obturages piece (3) obturages gas leakage between portion；
Pin (5), the pin (5) be used for by it is described obturage piece (3) obturage portion and the backboard (2) and the guide vane
(6) interconnecting piece is fixedly connected.
2. turbine casing seal structure according to claim 1, which is characterized in that one end of the backboard (2) has curved
Folding part obturages the end for obturaging portion of piece (3) described in bending part cladding.
3. turbine casing seal structure according to claim 1, which is characterized in that one end of the pin (5) has cap
Head, the diameter of the cap head are greater than the diameter of the pin hole of the interconnecting piece.
4. turbine casing seal structure according to claim 3, which is characterized in that the other end of the pin (5) passes through
Flaring, which is realized, to be fixed.
5. turbine casing seal structure according to claim 3, which is characterized in that the other end of the pin (5) passes through
Welding, which is realized, to be fixed.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910655984.XA CN110284929B (en) | 2019-07-19 | 2019-07-19 | Turbine cartridge receiver structure of obturaging |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910655984.XA CN110284929B (en) | 2019-07-19 | 2019-07-19 | Turbine cartridge receiver structure of obturaging |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN110284929A true CN110284929A (en) | 2019-09-27 |
| CN110284929B CN110284929B (en) | 2021-10-22 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910655984.XA Active CN110284929B (en) | 2019-07-19 | 2019-07-19 | Turbine cartridge receiver structure of obturaging |
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| CN (1) | CN110284929B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114165300A (en) * | 2021-10-20 | 2022-03-11 | 中国航发四川燃气涡轮研究院 | Turbine rear bearing floating structure capable of reducing thermal stress |
Citations (18)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1306575A (en) * | 1970-07-02 | 1973-02-14 | Westinghouse Electric Corp | Segmented seal assembly for axial flow turbines |
| US5320484A (en) * | 1992-08-26 | 1994-06-14 | General Electric Company | Turbomachine stator having a double skin casing including means for preventing gas flow longitudinally therethrough |
| EP1156188A2 (en) * | 2000-05-16 | 2001-11-21 | General Electric Company | A leaf seal for gas turbine stator shrouds and a nozzle band |
| EP1002972B1 (en) * | 1998-11-19 | 2003-09-03 | Snecma Moteurs | Strip seal |
| JP2005090304A (en) * | 2003-09-16 | 2005-04-07 | Ishikawajima Harima Heavy Ind Co Ltd | Seal plate structure |
| CN2908790Y (en) * | 2006-04-29 | 2007-06-06 | 上海汽轮机有限公司 | Sealing device for stator component of turbine |
| JP2011163304A (en) * | 2010-02-15 | 2011-08-25 | Babcock Hitachi Kk | Duct seal structure and method for forming the same seal structure |
| CN103649469A (en) * | 2011-07-22 | 2014-03-19 | 斯奈克玛 | Stator wheel for a turbine engine and turbine or compressor comprising such a stator wheel |
| CN104373965A (en) * | 2014-10-28 | 2015-02-25 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Transition section rear sealing structure |
| CN204419280U (en) * | 2015-01-06 | 2015-06-24 | 中国航空工业集团公司沈阳发动机设计研究所 | Seal structure between a kind of high and low pressure turbine stator |
| US20150354384A1 (en) * | 2012-12-29 | 2015-12-10 | United Technologies Corporation | Bumper for seals in a turbine exhaust case |
| CN205000996U (en) * | 2015-09-24 | 2016-01-27 | 中航商用航空发动机有限责任公司 | Quick -witted casket front end seal device and aeroengine between ring, turbine stage obturages |
| CN105298561A (en) * | 2015-11-20 | 2016-02-03 | 沈阳黎明航空发动机(集团)有限责任公司 | Packing-off piece installation device of turbine stator blades and use method of packing-off piece installation device |
| CN107013257A (en) * | 2015-10-20 | 2017-08-04 | 通用电气公司 | The arc-like sheet seal of the trough of belt of turbine |
| CN206647140U (en) * | 2017-04-07 | 2017-11-17 | 中国航发沈阳发动机研究所 | Turborotor bullet formula seal structure |
| US20180119558A1 (en) * | 2016-10-31 | 2018-05-03 | United Technologies Corporation | W-seal shield for interrupted cavity |
| US20180238192A1 (en) * | 2017-02-23 | 2018-08-23 | Safran Aircraft Engines | Connection between a circular shell and a radial structural arm of a turbomachine, comprising a seal and its support |
| US20190093495A1 (en) * | 2017-09-25 | 2019-03-28 | United Technologies Corporation | Hydrostatic seal pinned cartridge |
-
2019
- 2019-07-19 CN CN201910655984.XA patent/CN110284929B/en active Active
Patent Citations (18)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1306575A (en) * | 1970-07-02 | 1973-02-14 | Westinghouse Electric Corp | Segmented seal assembly for axial flow turbines |
| US5320484A (en) * | 1992-08-26 | 1994-06-14 | General Electric Company | Turbomachine stator having a double skin casing including means for preventing gas flow longitudinally therethrough |
| EP1002972B1 (en) * | 1998-11-19 | 2003-09-03 | Snecma Moteurs | Strip seal |
| EP1156188A2 (en) * | 2000-05-16 | 2001-11-21 | General Electric Company | A leaf seal for gas turbine stator shrouds and a nozzle band |
| JP2005090304A (en) * | 2003-09-16 | 2005-04-07 | Ishikawajima Harima Heavy Ind Co Ltd | Seal plate structure |
| CN2908790Y (en) * | 2006-04-29 | 2007-06-06 | 上海汽轮机有限公司 | Sealing device for stator component of turbine |
| JP2011163304A (en) * | 2010-02-15 | 2011-08-25 | Babcock Hitachi Kk | Duct seal structure and method for forming the same seal structure |
| CN103649469A (en) * | 2011-07-22 | 2014-03-19 | 斯奈克玛 | Stator wheel for a turbine engine and turbine or compressor comprising such a stator wheel |
| US20150354384A1 (en) * | 2012-12-29 | 2015-12-10 | United Technologies Corporation | Bumper for seals in a turbine exhaust case |
| CN104373965A (en) * | 2014-10-28 | 2015-02-25 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Transition section rear sealing structure |
| CN204419280U (en) * | 2015-01-06 | 2015-06-24 | 中国航空工业集团公司沈阳发动机设计研究所 | Seal structure between a kind of high and low pressure turbine stator |
| CN205000996U (en) * | 2015-09-24 | 2016-01-27 | 中航商用航空发动机有限责任公司 | Quick -witted casket front end seal device and aeroengine between ring, turbine stage obturages |
| CN107013257A (en) * | 2015-10-20 | 2017-08-04 | 通用电气公司 | The arc-like sheet seal of the trough of belt of turbine |
| CN105298561A (en) * | 2015-11-20 | 2016-02-03 | 沈阳黎明航空发动机(集团)有限责任公司 | Packing-off piece installation device of turbine stator blades and use method of packing-off piece installation device |
| US20180119558A1 (en) * | 2016-10-31 | 2018-05-03 | United Technologies Corporation | W-seal shield for interrupted cavity |
| US20180238192A1 (en) * | 2017-02-23 | 2018-08-23 | Safran Aircraft Engines | Connection between a circular shell and a radial structural arm of a turbomachine, comprising a seal and its support |
| CN206647140U (en) * | 2017-04-07 | 2017-11-17 | 中国航发沈阳发动机研究所 | Turborotor bullet formula seal structure |
| US20190093495A1 (en) * | 2017-09-25 | 2019-03-28 | United Technologies Corporation | Hydrostatic seal pinned cartridge |
Non-Patent Citations (4)
| Title |
|---|
| 孙炳津: "燃机机匣安装边密封性研究", 《中国优秀博硕士学位论文全文数据库(硕士)工程科技Ⅱ辑》 * |
| 宋丙新等: "基于瞬态动力学的某型航空发动机涡轮后机匣外封严环固定螺钉脱落故障分析及改进", 《航空维修与工程》 * |
| 李莹等: "燃机涡轮机匣改进结构后可靠性分析", 《第十五届中国科协年会第13分会场：航空发动机设计、制造与应用技术研讨会论文集》 * |
| 来纯强: "典型机匣安装边结构密封特性研究", 《中国优秀博硕士学位论文全文数据库(硕士)工程科技Ⅱ辑》 * |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114165300A (en) * | 2021-10-20 | 2022-03-11 | 中国航发四川燃气涡轮研究院 | Turbine rear bearing floating structure capable of reducing thermal stress |
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| Publication number | Publication date |
|---|---|
| CN110284929B (en) | 2021-10-22 |
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